Accession Number:

ADA102170

Title:

Determination of Aerodynamically Adequate Fillet Geometry in Turbocompressor Blade Rows

Descriptive Note:

Final rept. Apr 1980-Feb 1981

Corporate Author:

AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1981-05-01

Pagination or Media Count:

45.0

Abstract:

A method for determining the fillet radius likely to prevent separation of the corner flow at the intersection of an airfoil and a hub or shroud where no relative motion or gap is present is described. A computer program was written which, from the physical dimensions of the blading and the flow characteristics at the blading entrance and exit, calculates the corner boundary layer parameters allowing the prediction of the required fillet radius. An incompressible turbulent flow, with the influence of endwall boundary layer secondary flow on the development of the corner boundary layer, is considered.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE